System and apparatus for launching a missile

ABSTRACT

A launch apparatus for launching a missile includes a launching tube extending in a longitudinal direction. The launching tube has an outlet opening at a first end. An acceleration device arranged in the region of a second end of the launching tube includes a gas generator to generate a gas mass flow, and a bag formed from a textile fabric. The bag is coupled to a diffuser of the gas generator via an end opening and inflates longitudinally by the gas mass flow generated by the gas generator to accelerate the missile. The bag has a gas permeability within a range of between 10 l dm−2 min−1 and 30 l dm−2 min−1. When inflated, a cross section of the bag alternatively or additionally tapers from the end opening to a minimal cross section along the longitudinal direction and increases in size to an end opposite the end opening.

The present invention relates to a launch apparatus and a launch system for launching a missile, and to an acceleration device for a launch apparatus.

Unmanned missiles, such as reconnaissance drones, rockets or the like, are often launched from launching tubes or ejection apparatuses. Such ejection apparatuses typically have a guide tube in which the missile can be accommodated and an acceleration device. By means of the acceleration device, the missile is accelerated to a desired minimum speed within the guide tube such that the missile is capable of flight at least for a certain distance after leaving the guide tube, possibly until an engine is activated.

U.S. Pat. No. 8,505,430 B2 describes an ejection apparatus having a guide tube and an acceleration device arranged at a base of the guide tube, which acceleration device has a gas generator and a sabot. Together with the guide tube, the sabot defines a pressure chamber in which the gas generator is arranged, it being possible for a propellant gas to be released by means of the gas generator to accelerate the sabot in the direction of an outlet opening of the guide tube. The sabot is connected to the guide tube by means of a catching line to prevent the sabot from being ejected out of the guide tube in an uncontrolled manner.

WO 2017/037699 A1 describes a system for launching a missile having a guide tube in which the missile is accommodated and an acceleration device in the form of a gas reservoir coupled to and detachable from the missile, in which gas reservoir compressed air for accelerating the missile is stored.

EP 0 380 657 B1 also describes an ejection apparatus having a guide tube open on one side and an acceleration device that has a gas-impermeable bag and a gas generator, the bag being fastened to the gas generator with an open end in a sealing manner. The bag is can be inflated from a folded state by means of the gas generator in order to accelerate a missile in the guide tube.

An object of the present invention is to provide improved solutions for launching a missile.

This object is achieved by the subject matter of the independent claims.

Advantageous embodiments and further developments follow from the dependent claims, which refer back to the independent claims, in conjunction with the description.

According to a first aspect of the invention, a launch apparatus for launching a missile is provided. The launch apparatus comprises a launching tube, which extends in a longitudinal direction, for accommodating the missile, which launching tube has an outlet opening at a first end, and an acceleration device arranged in the region of a second end of the launching tube. The acceleration device comprises a gas generator that can be activated to generate a gas mass flow, and a bag formed from a textile fabric, which bag is coupled to a diffuser of the gas generator via an end opening and can be inflated along the longitudinal direction by the gas mass flow that can be generated by the gas generator to accelerate the missile. The bag has a gas permeability within a range of between 10 l dm⁻² min⁻¹ and 30 l dm⁻² min⁻¹.

An idea on which this aspect of the invention is based is to accelerate a missile in a launching tube by means of a bag that can be inflated by a gas generator, the bag having a certain permeability for the propellant gas that can be released by the gas generator, in particular within a range of between 10 l dm⁻² min⁻¹ and 30 l dm⁻² min⁻¹. During the highly unsteady process of inflating the bag, the gas permeability of the bag is negligible such that the missile in the launching tube is efficiently accelerated by the increasing volume of the bag and is ejected through the outlet opening. Within the range of gas permeability according to the invention, however, the bag deflates again relatively quickly after the missile is ejected from the launching tube, for example within a range of between 10 seconds and 2 minutes. Thus, the pressure in the bag begins to decrease substantially immediately after the missile has been ejected. This reduces the risk of unwanted, explosive gas escaping from the bag, for example as a result of damage when the launch apparatus is removed. This simplifies the operation of the launch apparatus and, at the same time, improves safety for an operator.

According to one embodiment, the textile fabric of the bag defines the gas permeability within a range of between 10 l dm⁻² min⁻¹ and 30 l dm⁻² min⁻¹. In particular, a weave density of the yarns forming the fabric, which may contain aramid fibres and/or polyamide fibres, for example, can be set in such a way that results in the desired gas permeability. Setting the gas permeability by means of the composition of the fabric itself offers the advantage that the bag can be manufactured with a high level of resistance to tearing and is therefore particularly robust.

According to a further embodiment, it is provided that the bag has one or a plurality of ventilation openings that define the gas permeability within a range of between 10 l dm⁻² min⁻¹ and 30 l dm⁻² min⁻¹. This facilitates the manufacture of the bag. Furthermore, a relatively large gas mass flow can be released through the ventilation openings, which is particularly advantageous in the case of large bags, for example within a bag volume range of between 8 litres and 30 litres.

According to a further embodiment, it is provided that, in an inflated state, a cross section of the bag tapers from the end opening to a minimal cross section along the longitudinal direction and increases in size again to an end opposite the end opening. In general, the bag can thus have a waisted shape along the longitudinal direction. This has the advantage that when the bag is inflated, a contact area between an inner surface of the launching tube and the bag and thus the friction between the bag and the launching tube is reduced. On the one hand, this helps to prevent damage to the bag. Furthermore, the transmission of force to the missile is thereby improved, although the maximum volume of the bag, which is limited by the inner surface of the launching tube, is not fully utilised.

According to a further embodiment, the launch apparatus has a plate sewn into a pocket of the bag, the pocket being formed at an end of the bag opposite the end opening. The plate can in particular have a circumferential shape that is designed to correspond to a circumferential shape defined by the inner surface of the launching tube. The plate is generally rigid and can in particular be made from a fibre composite material, for example a carbon fibre-reinforced plastics material, or from a metal material, such as an aluminium alloy or a steel alloy. The plate improves the transmission of force from the bag to the missile. The plate is accommodated in a closed volume that is defined by two textile layers of the bag. The layers defining the volume or the pocket form an end of the bag that is opposite the end opening with respect to the longitudinal direction, which end opening is coupled to the gas generator. The textile layers defining the bag are sewn together to close the volume. The plate is thus advantageously reliably fixed.

According to a further embodiment, it is provided that the acceleration device has a control module connected to the gas generator, which control module has a first communication interface for receiving control signals and a control device connected to the first communication interface, which control device is arranged to generate an activation signal for activating the gas generator based on the control signals. The communication interface can in particular be arranged for wired or wireless data transmission. For example, the communication interface can be arranged as a radio interface for receiving and transmitting radio signals in a predetermined frequency band. The control device can in particular have a processor, for example in the form of a CPU, an ASIC or an FPGA, and a non-volatile data memory, for example a flash memory. The control device can in particular be implemented as a microcontroller. In general, the control device is arranged to generate control commands or activation signals that cause the gas generator to generate the gas mass flow. The control module can optionally also have an electrical energy source, such as an accumulator or a battery. The control module advantageously facilitates remote triggering or remote actuation of the launch apparatus.

According to one embodiment, the launching tube is formed from a carbon fibre-reinforced plastics material, the first communication interface being formed by an antenna integrated into an outer surface of the launching tube or connected thereto. The antenna can be implemented, for example, by a conductor path structure printed on a printed circuit board, the printed circuit board being inserted into a depression defined by the outer surface of the launching tube. In general, the antenna can be laminated through a matrix material in which the carbon fibres are embedded. Accordingly, the antenna is integrated into the launching tube to save space and is reliably protected against mechanical damage. The integration of the antenna into the outer surface facilitates wireless signal transmission into the interior of the launching tube when using carbon fibre-reinforced plastics material, which in itself has a shielding effect for radio signals. However, the use of carbon fibre-reinforced plastics material for the launching tube has the advantage that it is mechanically particularly robust and yet light, which makes it easier to transport the launch apparatus.

The control module is preferably coupled to the gas generator in a mechanically detachable manner. For example, the gas generator and the control module can each have a flange portion, the flange portions being screwed together or fastened to one another via a snap fastener. Thus, the gas generator and the bag can be easily separated from the control module after use, that is after the bag has been inflated by the propellant gas released by the gas generator, and the control module can be coupled to a new gas generator. The operation of the launch apparatus is thus further simplified.

According to a second aspect of the invention, a launch apparatus for a missile is provided. Said launch apparatus comprises a launching tube, which extends in a longitudinal direction, for accommodating the missile, which launching tube has an outlet opening at a first end, and an acceleration device arranged in the region of a second end of the launching tube having a gas generator that can be activated to generate a gas mass flow, and a bag formed from a textile fabric, which bag is coupled to a diffuser of the gas generator via an end opening and can be inflated along the longitudinal direction by the gas mass flow that can be generated by the gas generator to accelerate the missile. According to this aspect of the invention, it is provided that, in an inflated state, a cross section of the bag tapers from the end opening to a minimal cross section along the longitudinal direction and increases in size again to an end opposite the end opening.

According to one embodiment, it is provided that, in an inflated state, the bag has the shape of a hyperboloid. The implementation of the bag having the shape of a hyperboloid provides surprisingly high mechanical strength, in particular resistance to tearing. At the same time, the friction surface between the bag and the inner surface of the launching tube is further reduced.

An idea on which this aspect of the invention is based is to accelerate a missile in a launching tube by means of a bag that can be inflated by a gas generator, the bag, when inflated by the gas generator, having a waisted shape along the longitudinal direction. This has the advantage that when the bag is inflated, a contact area between an inner surface of the launching tube and the bag and thus the friction between the bag and the launching tube is reduced. On the one hand, this helps to prevent damage to the bag. Furthermore, the transmission of force to the missile is thereby improved, although the maximum volume of the bag, which is limited by the inner surface of the launching tube, is not fully utilised.

According to one embodiment, it is provided that, in an inflated state, the bag has the shape of a hyperboloid. The implementation of the bag having the shape of a hyperboloid provides surprisingly high mechanical strength, in particular resistance to tearing. At the same time, the friction surface between the bag and the inner surface of the launching tube is further reduced.

According to one embodiment, the bag has a gas permeability within a range of between 10 l dm⁻² min⁻¹ and 30 l dm⁻² min⁻¹. The gas permeability of the bag can be defined, for example, by the textile fabric of the bag. In particular, a weave density of the yarns forming the fabric, which may contain aramid fibres and/or polyamide fibres, for example, can be set in such a way that results in the desired gas permeability. Setting the gas permeability by means of the composition of the fabric itself offers the advantage that the bag can be manufactured with a high level of resistance to tearing and is therefore particularly robust. Alternatively, it can be provided that the bag has one or a plurality of ventilation openings that define the gas permeability within a range of between 10 l dm⁻² min⁻¹ and 30 l dm⁻² min⁻¹. This facilitates the manufacture of the bag. Furthermore, a relatively large gas mass flow can be released through the ventilation openings, which is particularly advantageous in the case of large bags, for example within a bag volume range of between 8 litres and 30 litres.

According to a further embodiment, the launch apparatus has a plate sewn into a pocket of the bag, the pocket being formed at an end of the bag opposite the end opening. The plate can in particular have a circumferential shape that is designed to correspond to a circumferential shape defined by the inner surface of the launching tube. The plate is generally rigid and can in particular be made from a fibre composite material, for example a carbon fibre-reinforced plastics material, or from a metal material, such as an aluminium alloy or a steel alloy. The plate improves the transmission of force from the bag to the missile. The plate is accommodated in a closed volume that is defined by two textile layers of the bag. The layers defining the volume or the pocket form an end of the bag that is opposite the end opening with respect to the longitudinal direction, which end opening is coupled to the gas generator. The textile layers defining the bag are sewn together to close the volume. The plate is thus advantageously reliably fixed.

According to a further embodiment, it is provided that the acceleration device has a control module connected to the gas generator, which control module has a first communication interface for receiving control signals and a control device connected to the first communication interface, which control device is arranged to generate an activation signal for activating the gas generator based on the control signals. The communication interface can in particular be arranged for wired or wireless data transmission. For example, the communication interface can be arranged as a radio interface for receiving and transmitting radio signals in a predetermined frequency band. The control device can in particular have a processor, for example in the form of a CPU, an ASIC or an FPGA, and a non-volatile data memory, for example a flash memory. The control device can in particular be implemented as a microcontroller. In general, the control device is arranged to generate control commands or activation signals that cause the gas generator to generate the gas mass flow. The control module can optionally also have an electrical energy source, such as an accumulator or a battery. The control module advantageously facilitates remote triggering or remote actuation of the launch apparatus.

According to one embodiment, the launching tube is formed from a carbon fibre-reinforced plastics material, the first communication interface being formed by an antenna integrated into an outer surface of the launching tube or connected thereto. The antenna can be implemented, for example, by a conductor path structure printed on a printed circuit board, the printed circuit board being inserted into a depression defined by the outer surface of the launching tube. In general, the antenna can be laminated through a matrix material in which the carbon fibres are embedded. Accordingly, the antenna is integrated into the launching tube to save space and is reliably protected against mechanical damage. The integration of the antenna into the outer surface facilitates wireless signal transmission into the interior of the launching tube when using carbon fibre-reinforced plastics material, which in itself has a shielding effect for radio signals. However, the use of carbon fibre-reinforced plastic for the launching tube has the advantage that it is mechanically particularly robust and yet light, which makes it easier to transport the launch apparatus.

The control module is preferably coupled to the gas generator in a mechanically detachable manner. For example, the gas generator and the control module can each have a flange portion, the flange portions being screwed together or fastened to one another via a snap fastener. Thus, the gas generator and the bag can be easily separated from the control module after use, that is after the bag has been inflated by the propellant gas released by the gas generator, and the control module can be coupled to a new gas generator. The operation of the launch apparatus is thus further simplified.

According to a third aspect of the invention, an acceleration device for a launch apparatus for launching a missile is provided, the acceleration device having:

-   -   a gas generator that can be activated to generate a gas mass         flow;     -   a bag formed from a textile fabric, which bag is coupled to a         diffuser of the gas generator via an end opening and can be         inflated along the longitudinal direction by the gas mass flow         that can be generated by the gas generator to accelerate the         missile; and     -   a control module connected to the gas generator in a         mechanically detachable manner, which control module has a first         communication interface for receiving control signals and a         control device connected to the first communication interface,         which control device is arranged to generate an activation         signal for activating the gas generator based on the control         signals.

One idea on which this aspect of the invention is based is to provide a modular acceleration device in which a control module, which is arranged to activate the gas generator in order to inflate the bag to accelerate the missile, can be separated from the gas generator in a simple manner. For example, the gas generator and the control module can each have a flange portion, the flange portions being screwed together or fastened to one another via a snap fastener. Thus, the gas generator and the bag can be easily separated from the control module after use, that is after the bag has been inflated by the propellant gas released by the gas generator, and the control module can be coupled to a new gas generator. This simplifies the operation of the launch apparatus.

The communication interface can in particular be arranged for wired or wireless data transmission. For example, the communication interface can be arranged as a radio interface for receiving and transmitting radio signals in a predetermined frequency band. The control device can in particular have a processor, for example in the form of a CPU, an ASIC or an FPGA, and a non-volatile data memory, for example a flash memory. The control device can in particular be implemented as a microcontroller. In general, the control device is arranged to generate control commands or activation signals that cause the gas generator to generate the gas mass flow. The control module can optionally also have an electrical energy source, such as an accumulator or a battery. The control module advantageously facilitates remote triggering or remote actuation of the launch apparatus.

The acceleration device according to this aspect of the invention can be used in particular with a launch apparatus according to the first or the second aspect of the invention. The features and advantages disclosed for the first and the second aspect of the invention are thus also disclosed for the third aspect of the invention and vice versa.

According to a fourth aspect of the invention, a launch system for launching a missile is provided. The launch system has a launch apparatus according to the first or the second aspect of the invention, the acceleration device of the launch apparatus being implemented according to the third aspect of the invention. The system further comprises an operating device having an operating interface, a signal generating device connected to the operating interface for generating control signals, and a second communication interface that is arranged to transmit signals to the first communication interface.

The signal generating device can in particular be implemented as a microcontroller or generally be implemented with a processor and a non-volatile data memory. The user interface can, for example, be a simple pushbutton or a graphical interface, for example in the form of a touch display. The second communication interface can, in a similar manner to the first communication interface, be arranged for wired or wireless signal transmission, for example in the form of a radio interface. The operating device is used to activate the gas generator remotely by a user issuing a corresponding command via the user interface. Based on this command, the signal generating device generates a control signal that is transmitted to the first communication interface of the control module via the second communication interface. Based on this control signal, the control device generates an activation signal, for example in the form of an electrical pulse, by means of which the gas generator is activated. The gas generator then releases a gas mass flow that inflates the sack at high speed and thereby accelerates the missile, for example in the form of a rocket.

The gas generator can be implemented according to all aspects of the invention, for example as a hybrid gas generator. In this case, the gas generator comprises a high-pressure gas reservoir that is separated from the diffuser via a first separating disc and contains propellant gas, for example argon or helium, and a combustible propellant charge that is separated from the high-pressure gas reservoir via a second separating disc. The propellant charge contains an igniter that can be ignited by an electrical pulse and can thereby cause the propellant charge to burn up. When the propellant charge burns up, the second separating disc bursts and induces a pressure wave that propagates through the gas reservoir. The pressure wave destroys the first separating disc, as a result of which the gas stored in the gas reservoir and the gases produced by the burnup can escape into the diffuser and flow into the bag via the end opening. Alternatively, a hot gas generator or a cold gas generator can also be provided.

With regard to directional references and axes, in particular directional references and axes that relate to the course of physical structures, a course of an axis, a direction or a structure ‘along’ another axis, direction or structure is, in this case, understood to mean that these, in particular the tangents resulting in a respective location of the structures, each run at an angle of less than 45 degrees, preferably less than 30 degrees and particularly preferably parallel to one another.

With regard to directional references and axes, in particular directional references and axes that relate to the course of physical structures, a course of an axis, a direction or a structure ‘transverse’ to another axis, direction or structure is, in this case, understood to mean that these, in particular the tangents resulting in a respective location of the structures, each run at an angle of greater than or equal to 45 degrees, preferably greater than or equal to 60 degrees and particularly preferably perpendicular to one another.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is a schematic view of a launch system according to an embodiment of the invention, a launch apparatus of the system being shown in a schematic sectional view with a missile accommodated therein before the missile is launched;

FIG. 2 is a schematic sectional view of the launch apparatus shown in FIG. 1 during the launch of the missile;

FIG. 3 is a schematic sectional view of the launch apparatus shown in FIG. 2 at a later point in time during the launch of the missile;

FIG. 4 is a schematic sectional view of a bag of a launch apparatus according to an embodiment of the invention;

FIG. 5 is a schematic partial view of a bag of a launch apparatus according to an embodiment of the invention in a sectional view;

FIG. 6 is a schematic sectional view of an acceleration device according to an embodiment of the invention; and

FIG. 7 is a schematic sectional view of a launch apparatus according to a further embodiment of the invention during the launch of a missile.

In the drawings, identical reference signs designate identical or functionally identical components, unless stated otherwise.

FIG. 1 shows an example of a launch system 100 for launching a missile F. The system 100 has a launch apparatus 1 and an operating device 110. The launch apparatus 1 has a launching tube 10, an acceleration device 2 and an optional control module 3.

The launching tube 10 serves to accommodate the missile F, for example in the form of a rocket or a drone, and to guide the missile F during the launch. In FIG. 1, the missile F is shown, by way of example, as a rocket and can generally have its own propulsion. As shown schematically in FIG. 1, the launching tube 10 extends in a longitudinal direction L. The launching tube 10 has an outlet opening 11 at a first end 10A and an optional base 12 that can, for example, be attached to the launching tube 10 in a mechanically detachable manner at an end 10B opposite the longitudinal direction L. The launching tube 10 has an inner surface 10 i defining an interior and an oppositely oriented outer surface 10 e. The inner surface 10 i can, for example, define a circular or a rectangular inner cross section of the launching tube 10. The launching tube 10 can be formed, for example, from a fibre composite material, in particular a carbon fibre-reinforced plastics material, CFRP for short.

The acceleration device 2 is shown merely schematically in FIG. 1 and has a gas generator 20, a bag 21 and the control module 3. FIG. 6 shows, by way of example, a schematic sectional view of the acceleration device 2.

The gas generator 20 is used to generate a gas mass flow. In particular, the gas generator 20 can be activated in order to suddenly release a gas mass flow or a gas volume. The gas generator 20 shown by way of example in FIG. 6 is designed as a so-called hybrid gas generator and has a diffuser 22, a high-pressure gas reservoir 24, a propellant charge 26 and an igniter 28. The high-pressure gas reservoir 24 is a closed volume separated from the diffuser 22 by a first separating disc 24A and from the propellant charge 26 by a second separating disc 24B, in which closed volume a gas, for example helium, argon, nitrogen or another inert gas, is stored, for example with a pressure within a range of between 200 bar and 600 bar at ambient temperature. The propellant charge 26 contains an explosive or combustible material that can be activated by the igniter 28. The diffuser 22 is implemented as an approximately dome-shaped component that is fitted over the high-pressure gas reservoir 24 and has a plurality of openings 22A. To activate the gas generator 20, the igniter 28 is ignited, for example by means of an electrical pulse. As a result, the activation energy necessary for the chemical reaction is supplied to the propellant charge 28 such that the propellant charge 26 burns up. This causes the second separating disc 24B to burst and induces a pressure wave that propagates through the gas contained in the high-pressure reservoir 24. The pressure wave destroys the first separating disc 24A, as a result of which the gas stored in the gas reservoir and the explosion gases escape as propellant gas into the diffuser 22 through the openings 22A. Of course, alternative designs of the gas generator 20 are also conceivable. For example, a hot gas generator without a high-pressure gas reservoir 24 or a cold gas generator without a propellant charge 28 can also be provided.

The bag 21 is coupled to the diffuser 22 of the gas generator 20 via an end opening 21A such that, as a result of the activation of the gas generator 20, the propellant gas can flow into the bag 21 through the openings 22A of the diffuser 22 via the end opening 21 in order to inflate said bag. FIGS. 3, 4 and 7 show the bag 21 by way of example and schematically in an inflated state. The bag 21 has a tubular shape when inflated. In particular, the bag 21 extends between the end opening 21A and an end face portion or end 21B opposite thereto having a jacket portion 21C defining a cross section d21 of the bag 21. In an inflated state, the jacket portion 21C can, for example, define a cross section d21 that is constant between the end opening 21A and the end face portion 21B, as is shown in FIGS. 3 and 4 by way of example. However, it is also conceivable for the cross section d21 of the bag 21 to taper from the end opening 21A to a minimal cross section in the direction of the end face portion 21B and for it to increase in size again up to the end face portion 21B. Accordingly, the jacket portion 21C has a waisted shape with respect to the longitudinal direction L when inflated. This is shown by way of example in FIG. 7, in which the jacket portion 21C has the shape of a hyperboloid as an example of a waisted shape.

The bag 21 is formed from a textile fabric. The fabric can be woven from yarns which have, for example, aramid fibres, polyamide fibres, polyester fibres or the like. The bag 21 can in particular have a certain gas permeability, for example within a range of between 10 l dm⁻² min⁻¹ and 30 l dm⁻² min⁻¹. This gas permeability can be set, for example, by means of the weave density of the textile fabric or generally defined by the fabric. For example, a fabric as described in EP 0 665 313 A1 or another fabric known to those skilled in the art having such gas permeability can be used. Alternatively or additionally, one or a plurality of ventilation openings 23 can be incorporated into the bag 21, for example into the jacket portion 21C, in order to set the desired gas permeability within a range of between 10 l dm⁻² min⁻¹ and 30 l dm⁻² min⁻¹, as is shown by way of example in FIG. 4.

As shown by way of example in FIG. 5, a pocket 25 in which a plate 27 is accommodated can be formed on the end face portion 21B of the bag 21 between two textile layers 25A, 25B that are sewn together. The plate 27 is thus sewn between the textile layers 25A, 25B or into the pocket 25. The plate 27 is rigid. For example, the plate 27 can be formed from a metal material, for example titanium, aluminium, steel or such alloys, or from a fibre composite material. The plate 27 can, for example, have a circumference corresponding to the inner surface 10 i of the launching tube 10.

As shown schematically and by way of example in FIG. 6, the bag 21 is coupled to the diffuser 22 via its end opening 21A. In particular, the diffuser 22 is inserted into the end opening 21A of the bag 21 such that the openings 22A of the diffuser 22 are connected to the interior of the bag 21 in a fluid-conducting manner. As shown by way of example in FIG. 6, the jacket portion 21C of the bag 21 can be mechanically attached to the diffuser 21 in the region of the end opening 21A by means of a clamp 29. In FIG. 6, the bag 21 is shown schematically in a folded state. In this case, individual longitudinal regions of the jacket portion 21C of the bag 21 are placed against one another, for example in the form of a zigzag fold, as a result of which the volume of the bag 21 is reduced compared to the inflated state and substantially defined by the volume of the textile fabric and optionally by the volume of the plate 27.

The optional control module 3 has a control device 30, a first communication interface 31, an optional electrical energy storage unit 32, for example in the form of a battery or an accumulator, and an optional capacitor 33. These components can in particular be arranged or accommodated in a common housing 35.

The control device 30 can in particular have a processor, for example in the form of a CPU, an ASIC or an FPGA, and a non-volatile data memory, for example a flash memory. The control device 30 can, for example, be implemented as a microcontroller.

The first communication interface 31 is generally arranged for signal transmission, in particular for wireless or wired signal transmission, and can be designed, for example, as a radio interface. It is also conceivable to implement the first communication interface 31 as a wired interface, for example as a serial bus interface. The first communication interface 31 is connected to the control device 30.

As can also be seen in FIG. 6, the capacitor 33 is connected to the energy storage unit 32 and can be charged thereby. The capacitor 33 is also connected to the igniter 28 of the gas generator 33 in an electrically conductive manner. In addition, the capacitor 33 is functionally coupled to the control device 30. The control device 30 is arranged to generate an activation signal that causes the capacitor 33 to discharge. The igniter 28 is ignited by the discharging of the capacitor 33, and the gas generator 20 is thus activated. Of course, instead of a capacitor 33, other triggers for igniting the igniter 28 are also conceivable, which triggers can be actuated by an activation signal from the control device 30. The gas generator 20 can also be activated directly by means of the activation signal, for example in the case of a cold gas generator, a valve of the high-pressure gas reservoir can be opened. In general, the control device 30 is functionally connected to the gas generator 20 and is arranged to generate an activation signal for activating the gas generator 20.

The housing 35 can in particular have a flange portion 35A, which can be detachably connected to a flange portion 20A of the gas generator 20, for example by means of screwing, as is symbolically shown in FIG. 6. Alternatively, it is also conceivable to mechanically couple the housing 35 to the gas generator 20 by means of a bayonet lock or a clip lock. In general, the control module 3 is coupled to the gas generator 20 in a mechanically detachable manner.

As shown in FIG. 1, the acceleration device 2 is arranged in the region of the second end 10B of the launching tube 10. For example, the acceleration device 2 can be arranged at the base 12 of the launching tube 10. As is also shown schematically in FIG. 1, the first communication interface 31 of the control module 3 can be connected to an antenna 13. The antenna 13 is shown merely symbolically in FIG. 3. The antenna 13 is preferably integrated into the outer surface 10 e of the launching tube 10, for example by connecting a printed circuit board having conductor path structures that form the antenna 13 to the outer surface 10 e. In particular, if the launching tube 10 is made of CFRP, the signal transmission is facilitated in this way. It is also conceivable for the antenna 13 itself to form the first communication interface 31.

The operating device 110 is shown merely schematically in FIG. 1 and has an operating interface 111, a signal generating device 112 and a second communication interface 113.

The operating interface 111 serves to enable a user to enter commands and can be designed, for example, as a graphical interface, for example in the form of a touch display. It is also conceivable to implement the operating interface 111 as a simple button, switch or the like.

The signal generating device 112 is connected to the operating interface 111 and is arranged to generate a control signal based on an input made on the operating interface 111. The signal generating device 112 can be implemented, for example, with a processor, for example in the form of a CPU, an ASIC or an FPGA, and a data memory, for example in the form of a flash memory. It is also conceivable to implement the signal generating device 112 as an analogue electronic circuit.

The second communication interface 113 is connected to the signal generating device 112 and is arranged for wired or wireless signal transmission. For example, the second communication interface 113 can be implemented as a radio interface. Before the missile F is launched, the acceleration device 2 is arranged at the base 12 or at the second end 10B of the launching tube 10, the bag 21 being in a folded state. The missile F is placed on the acceleration device 2 in the launching tube 10. To launch the missile F, an operator (not shown) makes a corresponding input at the operating interface 111 of the operating device 110, which can be positioned, for example, at a distance from the launch apparatus 1. As a result of the input, the signal generating device 112 generates a control signal that is transmitted to the first radio interface 31 of the control module 3 via the second communication interface 113, for example as a radio signal. The control device 30 of the control module 3 generates, based on the control signal, an activation signal which activates the gas generator 20, for example in the manner described above. As shown schematically in FIG. 2, the bag 21 is inflated by the gas mass flow generated by the gas generator 20 and thereby expands in the longitudinal direction L, as a result of which the missile F is accelerated in the longitudinal direction L. As can be seen in FIGS. 3 and 7, the missile F is ejected through the outlet opening 11 of the launching tube 10 due to the acceleration.

As can be seen in FIG. 7, one advantage of the waisted design of the jacket portion 21C of the bag 21 is that a contact surface, and thus the friction between the bag 21 and the inner surface 10 i of the launching tube 10, is reduced. This reduces the frictional losses and thus increases the acceleration of the missile F in relation to the acceleration path.

The optional plate 27 advantageously improves the transmission of force from the bag 21 to the missile F during the acceleration of the missile F.

After the missile F has been launched or after the bag 21 has been inflated, said bag is advantageously automatically vented because it has a certain gas permeability, in particular within a range of between 10 l dm⁻² min⁻¹ and 30 l dm⁻² min⁻¹, which can be defined, for example, by the textile fabric of the bag 21 itself or by the ventilation openings 23. As a result, the bag 21 collapses relatively quickly from an inflated state after the acceleration device 2 is used. This facilitates handling and the quick removal of the acceleration device 2 from the launching tube 10.

Because the control module 3 is attached to the gas generator 20 in a mechanically detachable manner, a new gas generator 20 having an associated bag 21 can, after the gas generator 20 is used, be connected to the control module 3 in a simple and quick manner to form an acceleration device 2, which can then be reinserted into the launching tube 10.

Although the present invention has been explained by way of example using embodiments, it is not restricted thereto, but can be modified in a variety of ways. In particular, combinations of the above embodiments are also conceivable.

Without further elaboration, it is believed that one skilled in the art can, using the preceding description, utilize the present invention to its fullest extent. The preceding preferred specific embodiments are, therefore, to be construed as merely illustrative, and not limitative of the remainder of the disclosure in any way whatsoever.

In the foregoing and in the examples, all temperatures are set forth uncorrected in degrees Celsius and, all parts and percentages are by weight, unless otherwise indicated.

The entire disclosures of all applications, patents and publications, cited herein and of corresponding German application No. 102019003322.1, filed May 10, 2019, are incorporated by reference herein.

The preceding examples can be repeated with similar success by substituting the generically or specifically described reactants and/or operating conditions of this invention for those used in the preceding examples.

From the foregoing description, one skilled in the art can easily ascertain the essential characteristics of this invention and, without departing from the spirit and scope thereof, can make various changes and modifications of the invention to adapt it to various usages and conditions.

LIST OF REFERENCE SIGNS

-   1 launch apparatus -   2 acceleration device -   3 control module -   10 launching tube -   10A first end of the launching tube -   10B second end of the launching tube -   10 e outer surface of the launching tube -   10 i inner surface of the launching tube -   11 outlet opening -   12 base -   13 antenna -   20 gas generator -   20A flange portion -   21 bag -   21A end opening of the bag -   21 B end face portion/end of the bag -   21C jacket portion -   22 diffuser -   23 ventilation openings -   24 high pressure gas reservoir -   24A first separating disc -   24B second separating disc -   25 pocket -   25A, 25B textile layers -   26 propellant charge -   27 plate -   28 igniter -   29 clamp -   30 control device -   31 first communication interface -   32 electrical energy storage unit -   33 capacitor -   35 housing -   35A flange portion of the housing -   100 launch system -   110 operating device -   111 operating interface -   112 signal generating device -   113 second communication interface -   d21 cross section -   F missile -   L longitudinal direction 

1. Launch apparatus (1) for launching a missile (F), having: a launching tube (10) extending in a longitudinal direction (L) for accommodating the missile (F), which launching tube has an outlet opening (11) at a first end (10A); and an acceleration device (2) that is arranged in the region of a second end (10B) of the launching tube (10) and has a gas generator (20) that can be activated to generate a gas mass flow, and a bag (21) formed from a textile fabric, which bag is coupled to a diffuser (22) of the gas generator (20) via an end opening (21A) and can be inflated along the longitudinal direction (L) by the gas mass flow that can be generated by means of the gas generator (20) to accelerate the missile (F), the bag (21) being gas permeable within a range of between 10 l dm⁻² min⁻¹ and 301 dm⁻² min⁻¹.
 2. Launch apparatus (1) according to claim 1, characterised in that the textile fabric of the bag (21) defines the gas permeability within a range of between 10 l dm⁻² min⁻¹ and 30 l dm⁻² min⁻¹.
 3. Launch apparatus (1) according to claim 1, characterised in that the bag (21) has one or a plurality of ventilation openings (23) that define the gas permeability within a range of between 10 l dm⁻² min⁻¹ and 30 l dm⁻² min⁻¹.
 4. Launch apparatus (1) according to claim 1, characterised in that, in an inflated state, a cross section (d21) of the bag (21) tapers from the end opening (21A) to a minimal cross section along the longitudinal direction (L) and increases in size again to an end (21B) opposite the end opening (21A).
 5. Launch apparatus (1) for a missile (F), having: a launching tube extending in a longitudinal direction (L) for accommodating the missile (F), which launching tube has an outlet opening (11) at a first end (10A); and an acceleration device (2) that is arranged in the region of a second end (10B) of the launching tube (10) and has a gas generator (20) that can be activated to generate a gas mass flow, and a bag (21) formed from a textile fabric, which bag is coupled to a diffuser (22) of the gas generator (20) via an end opening (21A) and can be inflated along the longitudinal direction (L) by the gas mass flow that can be generated by means of the gas generator (20) to accelerate the missile (F), characterised in that, in an inflated state, a cross section (d21) of the bag (21) tapers from the end opening (21A) to a minimal cross section along the longitudinal direction (L) and increases in size again to an end (21B) opposite the end opening (21A).
 6. Launch apparatus (1) according to claim 4, characterised in that, in an inflated state, the bag (21) has the shape of a hyperboloid.
 7. Launch apparatus (1) according to claim 1, additionally having: a plate (27) sewn into a pocket (25) of the bag, the pocket (25) being formed at an end (21B) of the bag (21) opposite the end opening (21A).
 8. Launch apparatus (1) according to claim 1, characterised in that the acceleration device has a control module (3) connected to the gas generator (20), which control module has a first communication interface (31) for receiving control signals and a control device (30) connected to the first communication interface (31), which control device is arranged to generate an activation signal for activating the gas generator (20) based on the control signals.
 9. Launch apparatus (1) according to claim 8, characterised in that the launching tube (10) is formed from a carbon fibre-reinforced plastics material, and in that the first communication interface (31) is formed by an antenna (13) integrated into an outer surface (10 e) of the launching tube (10) or connected thereto.
 10. Launch apparatus (1) according to claim 8, characterised in that the control module (3) is coupled to the gas generator (20) in a mechanically detachable manner.
 11. Acceleration device (2) for a launch apparatus (1) for launching a missile (F), having: a gas generator (20) that can be activated to generate a gas mass flow; a bag formed from a textile fabric, which bag is coupled to a diffuser (22) of the gas generator (20) via an end opening (21A) and can be inflated by means of the gas mass flow that can be generated by means of the gas generator (20) to accelerate the missile (F) along the longitudinal direction (L); and a control module (3) connected to the gas generator (20) in a mechanically detachable manner, which control module has a first communication interface (31) for receiving control signals and a control device (30) connected to the first communication interface (31), which control device is arranged to generate an activation signal for activating the gas generator (20) based on the control signals.
 12. Launch system (100) for launching a missile (F), having: a launch apparatus (1) according to claim 8; and an operating device (110) having an operating interface (111), a signal generating device (112) connected to the operating interface (111) for generating control signals, and a second communication interface (113) that is arranged to transmit signals to the first communication interface (31). 